EI、Scopus 收录

## 留言板

 引用本文: 沈钧涛, 孙天风. 横向曲率对轴对称可压缩层流边界层的影响[J]. 力学学报, 1966, 9(2): 150-172.

 Citation: 北京大学, . EFFECT OF TRANSVERSE CURVATURE ON AXISYMMETRIC COMPRESSIBLE LAMINAR BOUNDARY LAYER[J]. Chinese Journal of Theoretical and Applied Mechanics, 1966, 9(2): 150-172.

## EFFECT OF TRANSVERSE CURVATURE ON AXISYMMETRIC COMPRESSIBLE LAMINAR BOUNDARY LAYER

• 摘要: 在轴对称细长体的绕流中,同物体当地横向曲率半径相比,粘性边界层厚度可能不是一个小量,而可能是大好多倍的量;这时在经典的Prandtl边界层方程中,以物体的横向曲率半径来代替边界层中任一一点到对称轴的距离,这种简化方法已不适用.因此,本文老虑了横向曲率对轴对称可压缩层流边界层流动的影响.首先研究了强影响区.在完全气体,Prandtl数等于1,粘性系数与温度成正比,以及压力梯度可以忽略等假定下,以一个表示横向曲率影响的量θ为小参数,将流函数展成幂级数,从而求得了强影响区域中的摩阻系数和热传递系数的渐近解.为了使这个展开式一致有效,文中用FLK方法消除了二级近似(卽级数中的第三项少在物面附近的奇异性。结果表明,对于幂次物体rw~xn来说,在强影响区,物面摩阻系数Cf和热传递系数St有下面的形式:Cf=4Ce/Rex Tw/Te x/rw cosφ{θ+[0.577-In(1+2n)]θ2}+O(θ3,St=1/2Cf.其次,采用动量积分关系方法研究了横向曲率在整个流动区域中的影响,文中采用Crocco变量下的形式,选择适当的切应力τ和速度μ的关系,求得了圆柱和圆锥的Cf, St表达式,井与弱影响区、强影响区的渐近解作了比较.

•  Probstein, R, F, and Elliott, D., The transverse curvature effect in eompressi6le axially symmetric laminar boundary Payer flow, jour.Aero. Sci,23, 3, 1956, 208-224. Seban, R. A. and Bond, R., Skin-friction and heat transfer characteristics of a laminar boundary layer on“cylinder in axial incomfsressihle flaw, Jour. Aero. Sci,18, 10, 1951, 671-675. Kelly, H. R., A note an the laminar boundary layer on a circular cylinder in axial incompressible flow, Jour. Aero. Sci,21, 9, 1954, 534. Glauerr, M. B. and Z.igtrthill, M. J., The axisymmetric boundary layer on a long thin cylinder, Proc.Ray. Sac., 5rries A, 230, 1955, 188-203. Stewartson, K,The asymptotic boundary layer an a circular cylinder in axial incompressible flow, Quart. Appl, Math., 13, 2, 1955, 113-122. Bourne, D. E. and Ltavies, D. R., Heat transfer through the laminar boundary layer an“circular cylinder in axial incompressible flaw, Quart. Jour, of Mech. and Appl. Math., 11, 1, 1958, 52-66. Yasuhara, M., Axisymmetric viscous flaw past very slender bodies of revolution, jour. Aero. Sci,29, 5. 1962. 667-679. Rant, J.. Skin friction of slender cones in hypersonic flow, AIAA Jour., 2, 4, 1964, 755-756. Stewartson, K,Viscous hypersonic flow past a slender cone, Phys. of Fluids, 7, 5, 1964, 667-675. Wei, M. H., Asymptotic boundary layer over a slender body of revolution in axial compressible flow. AIAA Jour.. 3. 5. 1965. 809-816. Гиневский,А.С.,Солодкин,Е.Е.,Влияние поперечной кривизны поверхности на характеристики осесимметричного турбулентного пограничного слоя,ПММ,22,6,1958,819-825. Гиневский,А.С.,Солодкин,Е.Е.,Влияние поперечной кривизны поверхности на характеристики неизотермического осесимметричного турбулентного пограничного слоя сжимаемого чаза,Изб,АН СССР,ОТН,Мех.ц Мащ.,1,1963,66-110. 钱学森(Tsien, H. S),The Poincaré-Lighthill-Kuo Method, in "Advances in Appl.Mech.", Vol. IV. Academic Press. New York.1956,281-349.

##### 计量
• 文章访问数:  1541
• HTML全文浏览量:  52
• PDF下载量:  359
• 被引次数: 0
##### 出版历程
• 刊出日期:  1966-06-25

/

• 分享
• 用微信扫码二维码

分享至好友和朋友圈